S135钻杆钢的拉扭复合加载疲劳行为

采用疲劳实验和回归分析相结合的方法,研究了S135钻杆钢在拉扭复合加载条件下的疲劳行为,并对疲劳断口进行了微观分析。结果表明:当τa/σeq=0.7时,由拉扭应力幅对应的当量应力表示的疲劳寿命公式可很好地描述S135钻杆钢的拉扭疲劳寿命规律;疲劳断口由疲劳源区、疲劳裂纹稳定扩展区和快速瞬断区组成,疲劳裂纹从试样表面萌生,并向试样内部扩展,且常为多疲劳源,不同疲劳源断口的连接和复合加载形成所谓的"屋脊"状特征;拉扭疲劳断裂试样裂纹源区的微观断口特征为明显的河流花样,裂纹扩展区的微观断口特征为疲劳条带与涟波状花样。     

航空铝合金原位腐蚀疲劳性能及断裂机理EI北大核心CSCD

为了研究不同腐蚀条件下2024铝合金的疲劳性能,首先设计搭建原位腐蚀疲劳平台,然后分别进行无腐蚀疲劳、预腐蚀疲劳和原位腐蚀疲劳实验,分析不同腐蚀疲劳条件下2024铝合金的疲劳断裂行为,最后利用扫描电镜(SEM)表征宏、微观断口特征,探究失效机理。结果表明:相同腐蚀环境和时间下,预腐蚀和原位腐蚀疲劳寿命分别为无腐蚀疲劳寿命的92%和42%;在原位腐蚀疲劳条件下,滑移带挤入、挤出导致表面粗糙度增加,吸附较多腐蚀介质,加剧蚀坑演化,易于裂纹萌生并形成多个裂纹源。裂纹的连通形成更大尺寸的损伤,并在材料内部快速扩展。预腐蚀和原位腐蚀疲劳试件断口观察到大量脆性疲劳条带,并且原位腐蚀疲劳条带平均间距约为无腐蚀疲劳条带间距的2倍,说明原位腐蚀疲劳条件下裂纹扩展速率更快。     

TNM-Ti Al合金室温高周疲劳性能研究

采用升降法与成组法对TNM-TiAl合金试样进行了应力比R=-1的室温拉压疲劳和R=0.1的室温拉伸疲劳试验，得到TNM-TiAl合金的P-S-N曲线，并对断口进行了分析。结果表明:TNM-TiAl合金对应力十分敏感，R=-1和R=0.1时的曲线整体呈较为平直的斜线，R=-1时的疲劳极限为414.7 MPa,R=0.1时的疲劳极限为285.6 MPa。R=0.1的S-N曲线远低于R=-1的S-N曲线;R=-1时，应力幅与疲劳寿命的关系满足Basquin方程。疲劳试件宏观断口较为粗糙，静态拉伸宏观断口平整，两者差异较大。拉伸断口整体分为裂纹萌生区与扩展区，其中起裂源均位于试样表面或板状试件的边角棱线处，起裂源区域包括γ相的解理断裂面、片层团的沿层解理面以及β₀相平整的穿晶断裂平面等特征。疲劳断口整体分为裂纹萌生区、扩展区与瞬断区，其中裂纹萌生区分为表面沿层起裂和γ相起裂。TNM-TiAl合金的疲劳断裂为脆性断裂，主要体现在扩展区上大量的片层团穿层断裂、扭折撕裂、γ相解理断裂和β₀相穿晶断裂。同寿命量级下，R=-1的断口与R=0.1的断口断裂类型...     

ZTA15铸造钛合金高周疲劳性能研究

目的 研究ZTA15铸造钛合金的高周疲劳性能及其疲劳断裂微观机理。方法 测试ZTA15铸造钛合金的室温轴向拉伸高周疲劳性能,并对合金的金相组织和断口形貌进行观察与分析。结果 随着应力比的提高,ZTA15铸造钛合金的疲劳强度相应提高,疲劳寿命也相应延长。应力比为?1、0.06、0.5时,相应ZTA15铸造钛合金的中值疲劳强度分别为341.5、512.5、643 MPa。疲劳断口形貌显示,疲劳裂纹多萌生于试棒的表面和次表面,裂纹萌生区呈类解理断裂特征。裂纹扩展区可以观察到明显的疲劳辉纹、扩展台阶和二次裂纹等典型特征。结论 疲劳失效机理和疲劳性能差异与合金的显微组织有一定的关系。应力比对疲劳性能的影响主要作用于疲劳裂纹的萌生和扩展阶段。     

6061-T6 铝合金激光焊接接头腐蚀疲劳裂纹扩展

目的研究6061-T6铝合金激光焊接接头的腐蚀疲劳裂纹扩展特性,并分析裂纹扩展的影响因素。方法利用光纤激光器,焊接尺寸为150 mm×100 mm×4 mm(焊接方向、横向、熔深方向)的6061-T6铝合金,采用SE(B)三点弯曲疲劳裂纹扩展试验并利用连续降K法,分别在空气和人工海水中进行疲劳裂纹扩展试验,通过使用金相显微镜(OE)和扫描电子显微镜(SEM),对金相结构进行观测分析。结果同样工艺参数的焊接接头,在海水中疲劳裂纹门槛值(4.063 016 MPa·m~(0.5))大于空气中的门槛值(3.479 166 MPa·m~(0.5));在疲劳裂纹扩展中速区(da/dN10~(-5) mm/cycle)时,海水焊接接头疲劳裂纹扩展速率大于空气中的,低速区(da/d N10~(-5) mm/cycle)则小于在空气中的。结论成形良好的焊缝、晶粒细小的焊缝组织有助于接头疲劳裂纹扩展性能的提高;中速区,海水中疲劳裂纹扩展速率偏大,主要是由腐蚀条件下焊缝裂纹尖端阳极溶解和交变载荷共同作用导致;低速区,海水中疲劳裂纹扩展速率偏小,主要原因是腐蚀产物堆积于疲劳裂纹扩展尖端,产生较强裂纹闭合效应。     

石油钻杆材料G105在不同条件下的疲劳断裂

采用国产PQ-6型旋转弯曲疲劳试验机研究钻杆管体材料G105的弯曲疲劳性能以及H_2S腐蚀和缺口对试样弯曲疲劳性能的影响,利用金相显微镜和扫描电子显微镜对光滑试样断口、缺口试样断口以及H_2S腐蚀后试样断口进行微观形貌分析。结果表明:在光滑试样的疲劳极限载荷作用下,经过H_2S腐蚀后的光滑试样的疲劳寿命和缺口试样的疲劳寿命相当,材料的疲劳寿命都从106降低至104;缺口试样在缺口的高应力集中效应下,加快疲劳裂纹形核过程。H_2S腐蚀对钻杆疲劳性能影响的主要作用在于氢原子在材料内缺陷处聚集引起材料疲劳性能降低,缺口和H_2S腐蚀都会加快疲劳裂纹的扩展。材料疲劳断裂主要是因为试样在交变应力的作用下上产生滑移最后致使位错塞积而导致的。     

热交换器不锈钢管束断裂失效分析

采用宏观分析、金相检验、断口宏观及微观分析以及能谱分析等方法,对某炼油厂裂化车间4台热交换器不锈钢管束先后发生大面积断裂的性质及原因进行了分析。结果表明:该热交换器管束断裂是由在交变载荷和腐蚀介质作用下发生的由外向内的腐蚀疲劳开裂引起的;腐蚀疲劳裂纹起始于管外壁的点蚀坑等应力集中处,促进腐蚀疲劳裂纹扩展的管束外部介质主要是Cl^-和H₂S;裂纹先以腐蚀疲劳开裂方式扩展,而后又呈典型的应力腐蚀开裂方式继续扩展,当应力腐蚀裂纹扩展达到管束断裂强度时便发生断裂。最后提出了预防管束断裂的措施及建议。     

梯度结构Al_2O_3-(W,Ti)C-TiN-Mo-Ni纳米金属陶瓷刀具材料的设计及制备

基于对高速硬切削时刀具应力和温度分布,以及刀具内部疲劳裂纹扩展仿真分析,提出一个组分含量分布和微观结构具有梯度特征的设计模型。通过韧性相的添加和梯度结构的引入,实现疲劳裂纹扩展速率的减缓,从而提高刀具寿命。采用二阶段热压烧结工艺制备出具有梯度结构的Al_2O_3-(W,Ti)C-TiN-Mo-Ni纳米复合刀具材料,并对其微观结构和力学性能进行研究。结果表明:所制备的梯度结构金属陶瓷材料表层硬度、内层的断裂韧度和抗弯强度分别达到19.258GPa,10.015MPa·m~(1/2)和1017.475MPa,满足高速硬切削刀具的性能要求。材料的断口出现韧窝和黏结相撕裂形成的断裂棱,有利于断裂韧度和抗弯强度的增强,从而提高刀具抗疲劳裂纹扩展能力。     

自回火对重轨钢疲劳裂纹扩展行为的影响

针对重轨钢在线淬火后自回火造成的抗疲劳裂纹扩展能力降低的问题,在淬火冷速分别为3℃/s、5℃/s、8℃/s,终冷温度为450℃条件下,研究了自回火对重轨钢疲劳裂纹扩展行为的影响,测算了疲劳裂纹扩展速率的Paris公式,采用扫描电镜及硬度计分别对自回火后钢轨的疲劳断口进行观察及硬度测试.结果表明:经过自回火后,钢轨的疲劳裂纹扩展速率增快、硬度降低,且自回火之前钢轨的淬火冷速越大,自回火后其硬度降低越显著,硬度的降低增加了裂纹扩展的可能性;自回火后钢轨在Ⅰ区的疲劳裂纹扩展速率远大于直接淬火试样,使钢轨疲劳裂纹扩展的整体进程缩短,这是疲劳裂纹扩展速率增快的重要原因.不同淬火冷速后的自回火试样在应力强度因子范围 ΔK(ΔK=Kmax-Kmin)为10 MPa·m1/2时,断口的疲劳辉纹、解理面和二次裂纹较少,河流花样数量较多、面积小、沟壑浅,而在ΔK=13.5 MPa·m1/2时,断口的疲劳辉纹间距增大,解理面和二次裂纹较多,河流花样数量增多、面积增大,疲劳裂纹扩展速率da/dN较快.     

Stellite12钴基合金的疲劳性能及其断裂机理研究

采用三点弯曲疲劳法测得光滑试样和直缺口试样的S-N曲线以研究Stellite12钴基合金的疲劳性能,并通过断口形貌观察进一步探究该钴基合金的断裂过程。结果表明:光滑试样的疲劳极限为545 MPa,约为原始抗弯强度1552 MPa的25.4%;直缺口试样的疲劳极限约为101MPa,约为静态抗弯强度517.6MPa的19.1%。对于疲劳敏感性,光滑试样与直缺口试样的疲劳敏感性分别为397和31。此外发现疲劳裂纹多萌生于近表层聚集的碳化物处,同时表面缺陷也可诱发疲劳裂纹的萌生。疲劳裂纹的扩展主要表现为碳化物的穿晶断裂,钴基体在应力比R=0.1的疲劳加载条件下虽表现出一定的韧性且呈现出较多的撕裂脊,但也呈现出一定的脆性断裂模式,因此疲劳裂纹扩展模式为真疲劳与静态疲劳的混合模式。     

Fatigue crack growth behavior of the simulated HAZ of 800 MPa grade high-performance steel

The present study focuses on the fatigue properties in the weld heat-affected zone (HAZ) of 800 MPa grade high-performance steel, which is commonly used in bridges and buildings. Single- and multi-pass HAZs were simulated by the Gleeble system. Fatigue properties were estimated using a crack propagation test under a 0.3 stress ratio and 0.1 load frequencies. The microstructures and fracture surfaces were analyzed by optical microscopy, scanning electron microscopy, and transmission electron microscopy. The results of the crack propagation test showed that the fatigue crack growth rate of coarse-grained HAZ (CGHAZ) was faster than fine-grained HAZ (FGHAZ), although both regions have identical fully martensite microstructures, because FGHAZ has smaller prior austenite grain and martensite packet sizes, which can act as effective barriers to crack propagation. The fatigue crack growth rate of intercritically reheated CGHAZ (ICCGHAZ) was the fastest among local zones in the HAZ, due to rapid crack initiation and propagation via the massive martensite-austenite (M-A) constituent.     

Corrosion fatigue behaviour and microstructural characterisation of G20Mn5QT cast steel in 3.5‐wt% NaCl solution

Corrosion fatigue behaviour and microstructural characterisation of G20Mn5QT cast steel are investigated in simulated seawater. Fractography is performed by using scanning electron microscopy (SEM). The macroscale fracture surface and microstructure of the failed specimen are acquired including the crack initiation, crack propagation, and pitting evolution. The maximum cyclic stress (S) versus number of cycles to failure (N) curves is derived by three‐parameter fatigue curve method. Fatigue life is predominantly controlled by the corrosion pitting‐induced crack initiation when tested in simulated seawater at lower stress levels. As the maximum cyclic stress is less than 185 MPa, the chloride ion erosion is the main influence factor, which affects the fatigue failure of the G20Mn5QT cast steel in simulated seawater.     

INITIAL FRACTURE MECHANISMS IN NICKEL ALLOYED PM STEEL

Abstract— Initial fatigue crack propagation mechanisms at near threshold conditions were studied for four nickel-alloyed, powder-metallurgy (PM) steels. Fatigue fracture surfaces were obtained by testing smooth rectangular specimens at 30 Hz and under constant amplitude and zero mean stress conditions. Materials based on Distaloy AE were used in two densities, namely 7.15 and 7.45 g/cm³.
All the fracture surfaces were composed of three morphological regions (i) a macrocrack initiation region Rl where cracks propagated preferentially through particles (ii) a macrocrack growth region R2 and (iii) an unstable crack growth region R3 where cracks propagated preferentially between particles. Initial fatigue crack growth, in region R1, was controlled by the propagation of short cracks whose dimensions were comparable to the material microstructure. The subsequent fatigue crack growth in regions R2 and R3 was controlled by ductile rupture between microvoids. Transparticle fracture in region R1 was independent of pore distribution, while interparticle fracture in regions R2 and R3 was dependent on pore distribution.     

High-cycle fatigue behaviour and mechanism analysis of a forged TiZr-based alloy

Fatigue resistance, particularly the endurance limit, is an important design consideration in engineering applications for TiZr-based alloys. The investigated Ti–20Zr–6Al–4?V (wt-%) alloy exhibited a high fatigue endurance limit of 775?MPa. Results showed that severe local stress concentration due to extensive dislocation pile-up at α/β interfaces was responsible for the crack initiation. A transition from a tensile mode to a shear mode crack was observed during crack propagation. Many striations as well as some micro-cracks which can improve the resistance to crack propagation exist in the stable crack-propagation region. A localised deviation between the crack-growth direction was also found, and this outcome combined with micro-cracks and tear ridge may be attributed to varied crystallographic orientations between different phases.     

Fatigue crack propagation in cellular metals

Two types of cellular metals were investigated: a closed-cell aluminium foam with a cell size of about 3.5 mm and densities ranging from 0.25 to 0.40 g/cm³ and hollow sphere structures made of a stainless steel (316L) with sphere sizes of 2 and 4 mm and a density of about 0.3 g/cm³. Fatigue and fatigue crack propagation tests were performed on these materials using an electro-dynamic resonance fatigue testing machine. The crack extension was monitored by a potential drop technique. Additionally, investigations were carried out inside the scanning electron microscope (SEM) using an in situ loading device. All tests were accompanied by local deformation measurements and fracture surface analyses. From the fatigue crack propagation tests it is evident that these materials show a relatively high Paris-Exponent m in the range of 6 to 25 compared to common ductile solid metals. Additional tests were performed to estimate the influence of crack closure, crack bridging and micro cracking on the da/dN versus ΔK curve for these materials. The in situ fatigue tests and the fracture surface analyses revealed a difference in the fatigue crack propagation mechanisms between the closed-cell foam and the hollow sphere structure: in the closed-cell foam a contiguous fatigue crack can be found, where in the case of the hollow sphere structure the fatigue crack propagation is concentrated in the vicinities of the sintering necks.     

喷丸强化对OCr13Ni8Mo2Al钢疲劳性能的影响

研究了表面喷丸强化后表面残余应力、表面粗糙度和表面层残余压应力场对0Cr13Ni8Mo2Al钢疲劳性能的影响.结果表明:0Cr13Ni8Mo2Al钢经喷丸强化后,在表面层残余压应力场的作用下疲劳裂纹源由表面被"驱赶"到表面强化层下,疲劳寿命得到显著提高.     

16Mn结构钢超高周疲劳性能研究

采用超声疲劳试验技术对16Mn结构钢超高周疲劳性能进行了研究，并用扫描电镜对疲劳断口进行了分析。结果显示16Mn结构钢在10^5-10^10周次范围内的S—N曲线呈阶梯型下降趋势，在10^6-10^8周次出现平台，平台对应应力幅约为220MPa．在平台应力以下，10^8周次以上超高周范围16Mn结构钢仍然发生疲劳断裂，不存在传统意义的疲劳极限。16Mn结构钢疲劳断口分析结果表明高周和超高周断裂试样的裂纹源主要从试件表面和次表面缺陷处萌生。10^7周次下超高周疲劳试样强度比常规试样疲劳强度低。     

金属疲劳断裂的声发射检测技术

疲劳断裂是金属结构的主要失效形式,通过金属疲劳断裂时声发射特征参数的提取,建立了声发射特征参数和裂纹扩展速率之间的关系,由试样的三点弯曲疲劳试验,证明采用声发射技术监测疲劳裂纹的扩展,不仅与疲劳裂纹扩展的变化规律相似,而且能实时的捕捉到疲劳裂纹的产生。     

Characterisation of fatigue fracture surfaces of friction stir channelling specimens tested at different temperatures

The fatigue fracture surfaces of friction stir channelling specimens tested at room temperature, 120 °C and 200 °C were observed in a scanning electron microscope (SEM) in order to analyse their morphology and the crack propagation mechanisms. Three different friction stir channelling conditions were tested and analysed. For all specimens tested the developing fatigue-crack has always initiated at the advancing side, namely on the boundary between the nugget and the thermo mechanically affected zone (TMAZ) into the interior of the specimen. The crack has propagated through the channel nugget with a path tangential to the advancing side. After the crack has reached the processed surface, a second crack initiated at the channel bottom. The fracture surfaces have shown a semi-elliptical shape crack front. This second crack has propagated uniformly through the base material. Fatigue crack propagation on the TMAZ was mainly characterised by fatigue striations. It was found, on most of the surfaces observed, a clear coexistence of the intergranular fracture mode and the transgranular fracture mode. A relationship between the fatigue testing temperature and the roughness of the fracture surfaces was found. The fracture surfaces roughness was considerably lower at a testing temperature of 200 °C for the three friction stir channelling conditions analysed.     

Effects of humidity and temperature on the fatigue behaviour of an extruded AZ61 magnesium alloy

Load‐controlled fatigue tests were performed at 20 and 50 °C using two relative humidity levels of 55 and 80% to characterize the influence of humidity and temperature on the fatigue behaviour of an extruded AZ61 magnesium alloy. Fatigue tests were also conducted at 150 °C. No significant variation in fatigue properties was noticed with respect to temperature over the range from 20 to 50 °C for both the humidity levels. Fatigue limits in the range 140–150 MPa were observed for relative humidity of 55%. Fatigue strength decreased significantly with increase in temperature to 150 °C. Further, a significant reduction in fatigue strength with a fatigue limit of ～110 MPa was observed with increase in relative humidity to 80% at 20 and 50 °C. The crack initiation and propagation remained transgranular under all test conditions. The fatigue fracture at low stress amplitudes and high relative humidity of 80% results from the formation of corrosion pits at the surface and their growth to a critical size for fatigue‐crack initiation and propagation. The observed reduction in fatigue strength at high humidity is ascribed to the effects associated with fatigue–environment interaction.